磁控进气道的临界焓提取率研究与数值验证  

Study on critical enthalpy extraction ratio and numerical validation for magnetohydrodynamic inlet

作　　者：陈瑞锋[1] 魏志军[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2011年第8期1808-1813,共6页Journal of Aerospace Power

摘　　要：为保证磁控进气道工作于起动状态,提出了临界焓提取率的概念,采用涡轮喷气发动机的模型对磁控进气道进行类比分析,推导得到了磁控进气道在临界起动状态下的模型.最后通过数值验算,磁控进气道的临界状态模型与数值结果符合较好,误差小于5.7%,可为磁控进气道的设计提供参考.To ensure that the magnetohydrodynamic （MHD） inlet works in starting state, the concept of critical enthalpy extraction ratio was proposed for the MHD inlet. The quasi-one dimensional model for the critical enthalpy extraction ratio state of MHD inlet was analyzed using the turbojet engine model, the variable cross-section pipe flow theory and the expressions of modified polytropic efficiencies. By comparison of this model with the compu rational fluid dynamics （CFD） method, the results show that this model fits good, and the error is less than 5.7%, thus providing a reference for design of the MHD inlet.

关 键 词：磁控进气道 临界焓提取率 起动状态 超燃冲压发动机 涡轮喷气发动机 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]